CN106585957A - Composite wing integral oil tank and manufacturing method thereof - Google Patents
Composite wing integral oil tank and manufacturing method thereof Download PDFInfo
- Publication number
- CN106585957A CN106585957A CN201611155283.2A CN201611155283A CN106585957A CN 106585957 A CN106585957 A CN 106585957A CN 201611155283 A CN201611155283 A CN 201611155283A CN 106585957 A CN106585957 A CN 106585957A
- Authority
- CN
- China
- Prior art keywords
- eyelid covering
- lid
- wing
- tank
- oil tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Rigid Or Semi-Rigid Containers (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention relates to a composite wing integral oil tank. The composite wing integral oil tank comprises upper coverings 1, lower coverings 2, crossbeams and wing ribs 5, wherein each of the crossbeams is arranged between the corresponding upper covering 1 and the corresponding lower covering 2, and is divided into a front crossbeam 3 and a rear crossbeam 4, and each of the front crossbeams 3 and the corresponding rear crossbeam 4 are arranged in the spanwise direction; the wing ribs 5 are arranged between the corresponding front crossbeam 3 and the corresponding rear crossbeam 4 in the navigation direction; a front edge oil tank access cover 9 is arranged between each wing oil tank front wall 10 and the corresponding front crossbeam 3; a wing oil tank box section is formed between the corresponding front crossbeam and the corresponding rear crossbeam; each oil tank access cover 7 and a corresponding maintenance access cover are arranged on one side close to the corresponding lower covering 2, of the corresponding box section; and each of the oil tank access covers 7 is connected with the corresponding lower covering 2 through a corresponding sealing support plate nut 21, and a fuel oil sealing ring 31 is arranged between each of the oil tank access covers 7 and the corresponding lower covering 2. According to the composite wing integral oil tank disclosed by the invention, the manufacturing cost of composite airplanes is greatly reduced, the structural utilization efficiency is improved, the assembling tooling is saved, the assembling time is shortened, the workload is reduced, and the large-scale production of full-composite wing integral oil tanks is realized.
Description
Technical field
The present invention relates to aircraft wing integral tank, especially a kind of composite wing integral tank and its processing side
Method.
Background technology
Conventional airplane wing tank is typically using aluminium alloy processing or the composite autoclave forming process of high price
Manufacture, inevitably using substantial amounts of securing member and drilling in such wing tank.Especially, for composite,
Substantial amounts of securing member and drilling mean the consumption in a large amount of specific purpose tools and man-hour, and bring the successional destruction of fiber and more
High damage probability, reduces wing tank utilization ratio and increased cost, and produces huge workload.
The content of the invention
For the shortcomings and deficiencies of conventional airplane wing tank, it is that a kind of composite wing is whole that the present invention is to be provided
Body fuel tank and its processing method, reach high structure utilization ratio, reduce workload, are easy to the sealing of integral tank and utilize.
In order to solve above-mentioned technical problem, the technical solution used in the present invention is：A kind of composite wing integral tank,
Including upper eyelid covering 1, lower eyelid covering 2, crossbeam, rib 5；Crossbeam is distributed between upper eyelid covering 1 and lower eyelid covering 2, be divided into front beam 3 with it is rear
Crossbeam 4, along spanwise arrangement, is distributed with rib 5, the He of wing tank front wall 10 on the course between front beam 3 and rear cross beam 4
Leading edge fuel tank flap 9 is distributed between front beam 3, wing tank box section is formed between crossbeam in front and back, box section is near lower eyelid covering 2 one
Side is provided with fuel tank flap 7 and safeguards lid, and fuel tank flap 7 is connected by sealing plate nut 21 with lower eyelid covering 2, is set between the two
There is fuel sealing circle 31.
Above-mentioned to safeguard that lid is divided into pitot installation and safeguards that lid 8 is safeguarded in lid 6 and flap control, pitot is installed and safeguarded
Lid 6 is located between wing end rib and fuel tank end rib, and flap control safeguards lid 8 between two ribs 5 of fuselage.
Brush one layer of resin in above-mentioned upper and lower eyelid covering inner side.
Above-mentioned resin is epoxy resin.
The processing method of above-mentioned composite wing integral tank is comprised the following steps：
Step 1：Upper eyelid covering 1, lower eyelid covering 2, front beam 3, rear cross beam 4, rib 5, pitot are installed and safeguards lid 6, oil
Case lid 7, flap control safeguard lid 8, leading edge fuel tank flap 9, wing tank front wall 10 by non-autoclave Technology into
Type.0～0.074MPa of briquetting pressure, 110 DEG C～120 DEG C of temperature；
Step 2：The inner side of upper eyelid covering 1, the inner side of lower eyelid covering 2 are respectively coated into one layer of resin, resin thickness 2mm～3mm；
Step 3：The each fuel tank flap 7 of lower eyelid covering 2 is installed into sealing plate nut 31, and sealing plate nut 31 is applied
One layer of anti-fuel sealing agent.
Step 4：Lower eyelid covering 2 and front beam 3, rear cross beam 4, rib 5, wing tank front wall 10 are carried out into cementing, solidification；
Step 5：The composite product of upper eyelid covering 1 and step 4 gained is carried out into cementing, solidification；
Step 6：The edge and seam that step 5 gained oil tank box section is carried out into internal three faces handing-over with anti-fuel sealing agent is outer
Line is sealed.
Step 7：Fuel tank flap 7, pitot is installed and safeguards that lid 6, flap control safeguards lid 8 and leading edge fuel tank flap
9 are arranged on lower eyelid covering 2.
For prior art, the invention has the beneficial effects as follows：Composite airplane manufacturing cost is substantially reduced, structure is improved
Utilization ratio, saves assembly tooling and time, reduces workload, realizes the scale metaplasia of full composite material integral wing tank
Produce.
Description of the drawings
Fig. 1 is composite wing integral tank structural representation；
Fig. 2 is composite wing integral tank (right side) internal structure schematic diagram；
Fig. 3 is connected profile for fuel tank flap 7 with eyelid covering under wing 2；
1 in figure：Upper eyelid covering, 2：Lower eyelid covering, 3：Front beam, 4：Rear cross beam, 5：Rib, 6：Pitot install safeguard lid,
7：Fuel tank flap, 8：Flap control safeguard lid, 9：Leading edge fuel tank flap, 10：Wing tank front wall, 21：Plate nut, 31：
Fuel sealing circle.
Specific embodiment
The present invention is described in further detail with reference to Figure of description.
A kind of composite wing integral tank, including upper eyelid covering 1, lower eyelid covering 2；It is distributed between upper eyelid covering 1 and lower eyelid covering 2
There is crossbeam, be divided into front beam 3 and rear cross beam 4, spanwise arrangement is distributed with the wing on the course between front beam 3 and rear cross beam 4
Rib 5, is distributed with leading edge fuel tank flap 9 between wing tank front wall 10 and front beam 3, between front beam 3 and rear cross beam 4 machine is formed
Wing oil tank box section, box section is provided with fuel tank flap 7 and safeguards lid near the side of lower eyelid covering 2, and fuel tank flap 7 is by sealing supporting plate spiral shell
It is female to be connected with lower eyelid covering 2, fuel sealing circle 31 is provided between the two, as shown in Figures 1 to 3.
Above-mentioned to safeguard that lid is divided into pitot installation and safeguards that lid 8 is safeguarded in lid 6 and flap control, pitot is installed and safeguarded
Lid 6 is located between wing end rib and fuel tank end rib, and flap control safeguards lid 8 between two ribs of fuselage.
One layer of resin is respectively brushed with the inner side of lower eyelid covering 2 in the inner side of above-mentioned upper eyelid covering 1.
Above-mentioned resin be epoxy resin, the epoxy resin trade mark for adopting for MGS companies L285/ (H285, H286 or
H287)
The processing method of above-mentioned composite wing integral tank is comprised the following steps：
Step 1：Upper eyelid covering 1, lower eyelid covering 2, front beam 3, rear cross beam 4, rib 5, pitot are installed and safeguards lid 6, oil
Case lid 7, flap control safeguard lid 8, leading edge fuel tank flap 9, wing tank front wall 10 by non-autoclave Technology into
Type.Briquetting pressure is not less than 0.074MPa, 110 DEG C～120 DEG C of temperature；
Step 2：The inner side of upper eyelid covering 1, the inner side of lower eyelid covering 2 are respectively coated into one layer of resin, resin thickness 2mm～3mm；
Step 3：The each fuel tank flap 7 of lower eyelid covering 2 is installed into sealing plate nut 31, and sealing plate nut 31 is applied
One layer of anti-fuel sealing agent.
Step 4：Lower eyelid covering 2 and front beam 3, rear cross beam 4, rib 5, wing tank front wall 10 are carried out into cementing, solidification；
Step 5：The composite product of upper eyelid covering 1 and step 4 gained is carried out into cementing, solidification；
Step 6：The edge and seam that step 5 gained oil tank box section is carried out into internal three faces handing-over with anti-fuel sealing agent is outer
Line is sealed.
Step 7：Fuel tank flap 7, pitot is installed and safeguards that lid 6, flap control safeguards lid 8 and leading edge fuel tank flap
9 are arranged on lower eyelid covering 2.
Each product is carbon fiber prepreg paving solidification and forms in above-mentioned steps 1, the carbon fiber prepreg trade mark of employing
For the one-way tape T700S-12K-50C/#2510 of Toray companies, fabric T700G-12K-31E/#2510, pressure 0～
0.074MPa, 110 DEG C～120 DEG C of temperature is solidified by composite cure profile, and solidification temperature is less than 120 DEG C, is solidified into
Type, treats that die surface is cooled to 35 DEG C～50 DEG C parts and comes out of the stove, the demoulding, cutting, Non-Destructive Testing.
Above-mentioned cementing adhesive used is epoxy adhesive, the trade mark for adopting for Henkel Corp. EA9360, room temperature is solid
Change, hardening time is 12h.
The above-mentioned anti-fuel sealing agent trade mark used is the WS8020RC-B2 of Beijing Ke Ai companies.
The present invention replaces traditional autoclave technological forming wing tank composite material parts, profit using non-autoclave technology generations
Composite material parts are assembled with consolidation techniques, it is to avoid the shortcomings and deficiencies of traditional wing tank, reach the high structure profit of fuel tank
With efficiency, the purpose of reduction workload.
The above is the preferred embodiment of the present invention, it is noted that for those skilled in the art
For, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications are also considered as
Protection scope of the present invention.
Claims (7)
1. a kind of composite wing integral tank, it is characterised in that：Including upper eyelid covering (1), lower eyelid covering (2)；Upper eyelid covering (1) with
Crossbeam is distributed between lower eyelid covering (2), is divided into front beam (3) and rear cross beam (4), spanwise arrangement, front beam (3) and rear horizontal stroke
Rib (5) is distributed with course between beam (4), leading edge fuel tank is distributed between wing tank front wall (10) and front beam (3)
Lid (9), forms wing tank box section between front beam (3) and rear cross beam (4), box section is provided with oil near lower eyelid covering (2) side
Case lid (7) and lid is safeguarded, fuel tank flap (7) is connected by sealing plate nut (21) with lower eyelid covering (2), sets between the two
There is fuel sealing circle (31).
2. composite wing integral tank according to claim 1, it is characterised in that：Safeguard that lid is divided into pitot peace
Dress safeguards that lid (8) is safeguarded in lid (6) and flap control, and pitot is installed and safeguards that lid (6) is located at wing end rib and fuel tank end
Between rib, flap control safeguards lid (8) between two ribs (5) of fuselage.
3. composite wing integral tank according to claim 1, it is characterised in that：Upper eyelid covering (1) inner side, lower eyelid covering
(2) one layer of resin is brushed in inner side.
4. composite wing integral tank according to claim 3, it is characterised in that：Resin is epoxy resin.
5. a kind of manufacture method of composite wing integral tank, it is characterised in that：Composite wing integral tank plus
Work method is comprised the following steps：
Step 1：Upper eyelid covering (1), lower eyelid covering (2), front beam (3), rear cross beam (4), rib (5), pitot are installed and safeguards mouth
Lid (6), fuel tank flap (7), flap control safeguard lid (8), leading edge fuel tank flap (9), wing tank front wall (10) by non-
Autoclave Technology molding；
Step 2：Upper eyelid covering (1) inner side, lower eyelid covering (2) inner side are respectively coated into one layer of resin, resin thickness 2mm～3mm；
Step 3：The each fuel tank flap (7) of lower eyelid covering (2) is installed into sealing plate nut (31), and will sealing plate nut (31)
Apply one layer of anti-fuel sealing agent；
Step 4：By lower eyelid covering (2) and front beam (3), rear cross beam (4), rib (5), wing tank front wall (10) carry out it is cementing,
Solidification；
Step 5：The composite product of upper eyelid covering (1) and step 4 gained is carried out into cementing, solidification；
Step 6：Step 5 gained oil tank box section is carried out into the edge of internal three faces handing-over with anti-fuel sealing agent and seam outside line is entered
Row sealing；
Step 7：Fuel tank flap (7), pitot are installed and safeguards that lid (6), flap control safeguard lid (8) and leading edge reservoir port
Lid (9) is on lower eyelid covering (2).
6. the manufacture method of composite wing integral tank according to claim 5, it is characterised in that：In step 1 into
Type 0～0.074MPa of pressure, 110 DEG C～120 DEG C of temperature.
7. the manufacture method of composite wing integral tank according to claim 5, it is characterised in that：Above-mentioned cementing institute
Using adhesive adopt EA9360, fuel sealing agent to adopt WS8020RC-B2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155283.2A CN106585957B (en) | 2016-12-14 | 2016-12-14 | Composite material wing integral oil tank and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155283.2A CN106585957B (en) | 2016-12-14 | 2016-12-14 | Composite material wing integral oil tank and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106585957A true CN106585957A (en) | 2017-04-26 |
| CN106585957B CN106585957B (en) | 2023-03-31 |
Family
ID=58802403
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611155283.2A Active CN106585957B (en) | 2016-12-14 | 2016-12-14 | Composite material wing integral oil tank and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106585957B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107140178A (en) * | 2017-06-05 | 2017-09-08 | 芜湖中科飞机制造有限公司 | The wing structure of basic trainer aircraft |
| CN107244409A (en) * | 2017-05-31 | 2017-10-13 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN107264817A (en) * | 2017-06-05 | 2017-10-20 | 芜湖中科飞机制造有限公司 | Wing tank |
| CN108033026A (en) * | 2017-11-29 | 2018-05-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of detachable wing tank of aircraft |
| CN108100227A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing tank calculation of pressure method for considering rib and influencing |
| CN109555860A (en) * | 2018-11-23 | 2019-04-02 | 中航通飞华南飞机工业有限公司 | A kind of full composite material second bonding wing tank encapsulating method |
| CN109902330A (en) * | 2018-11-12 | 2019-06-18 | 中航通飞研究院有限公司 | A kind of aerofoil and its strength calculation method of no stringer and rib web |
| CN110920913A (en) * | 2019-12-04 | 2020-03-27 | 中国航空工业集团公司成都飞机设计研究所 | Double-oil-tank structure of reinforced wall plate made of composite material with high aspect ratio |
| WO2022057115A1 (en) * | 2020-09-15 | 2022-03-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane wing fuel tank access cover and structure of peripheral area of access cover |
| CN114261506A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Composite material wing with integral oil tank |
| CN118560734A (en) * | 2024-08-05 | 2024-08-30 | 中航(成都)无人机系统股份有限公司 | Unmanned aerial vehicle wing integral oil tank structure and manufacturing method |
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| CN105102319A (en) * | 2013-03-26 | 2015-11-25 | 三菱重工业株式会社 | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
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| JP2011051517A (en) * | 2009-09-03 | 2011-03-17 | Mitsubishi Heavy Ind Ltd | Aircraft wing |
| CN202138536U (en) * | 2011-06-03 | 2012-02-08 | 哈尔滨飞机工业集团有限责任公司 | Integral wing oil tank sealing structure |
| CN105102319A (en) * | 2013-03-26 | 2015-11-25 | 三菱重工业株式会社 | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
| CN203806132U (en) * | 2014-05-06 | 2014-09-03 | 江西洪都航空工业集团有限责任公司 | Rain-proof sealing cover assembly |
| CN104369857A (en) * | 2014-10-15 | 2015-02-25 | 中航飞机股份有限公司西安飞机分公司 | Whole oil tank structure of airplane |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244409B (en) * | 2017-05-31 | 2019-08-09 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN107244409A (en) * | 2017-05-31 | 2017-10-13 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN107264817A (en) * | 2017-06-05 | 2017-10-20 | 芜湖中科飞机制造有限公司 | Wing tank |
| CN107140178A (en) * | 2017-06-05 | 2017-09-08 | 芜湖中科飞机制造有限公司 | The wing structure of basic trainer aircraft |
| CN108100227A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing tank calculation of pressure method for considering rib and influencing |
| CN108100227B (en) * | 2017-11-22 | 2021-01-08 | 中国航空工业集团公司西安飞机设计研究所 | Wing oil tank pressure calculation method considering wing rib influence |
| CN108033026A (en) * | 2017-11-29 | 2018-05-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of detachable wing tank of aircraft |
| CN109902330A (en) * | 2018-11-12 | 2019-06-18 | 中航通飞研究院有限公司 | A kind of aerofoil and its strength calculation method of no stringer and rib web |
| CN109902330B (en) * | 2018-11-12 | 2023-09-12 | 中航通飞华南飞机工业有限公司 | Airfoil without stringers and rib webs and strength calculation method thereof |
| CN109555860A (en) * | 2018-11-23 | 2019-04-02 | 中航通飞华南飞机工业有限公司 | A kind of full composite material second bonding wing tank encapsulating method |
| CN110920913A (en) * | 2019-12-04 | 2020-03-27 | 中国航空工业集团公司成都飞机设计研究所 | Double-oil-tank structure of reinforced wall plate made of composite material with high aspect ratio |
| WO2022057115A1 (en) * | 2020-09-15 | 2022-03-24 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane wing fuel tank access cover and structure of peripheral area of access cover |
| CN114261506A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Composite material wing with integral oil tank |
| CN114261506B (en) * | 2021-12-31 | 2024-06-07 | 中国航空工业集团公司西安飞机设计研究所 | Composite wing with integral oil tank |
| CN118560734A (en) * | 2024-08-05 | 2024-08-30 | 中航(成都)无人机系统股份有限公司 | Unmanned aerial vehicle wing integral oil tank structure and manufacturing method |
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